螺旋桨滑流对高升力构型影响的数值计算

杨龙源; 盛云逸; 崔天昱; 杨永

doi:10.7638/kqdlxxb-2024.0090

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螺旋桨滑流对高升力构型影响的数值计算

研究论文 | 更新时间：2026-05-28

- 螺旋桨滑流对高升力构型影响的数值计算
- Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations
- 空气动力学学报 2025年43卷第5期页码：41-50
- 作者机构：
  
  西北工业大学飞行器基础布局全国重点实验室,西安,710072
- 作者简介：
  
  杨龙源（1999—），男，广西贺州人，研究生，研究方向：飞行器多学科耦合数值计算. E-mail：qfdlylyuan@163.com
  杨永*，教授，研究方向：空气动力学、流体力学、飞行器多学科耦合数值计算. E-mail：yyang@nwpu.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0090
  中图分类号： V211.3
- 纸质出版：2025
- 稿件说明：
移动端阅览
杨龙源, 盛云逸, 崔天昱, 等. 螺旋桨滑流对高升力构型影响的数值计算[J]. 空气动力学学报, 2025, 43(5): 41−50.

YANG Longyuan, SHENG Yunyi, CUI Tianyu, et al. Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations[J]. 2025, 43(5): 41-50.
杨龙源, 盛云逸, 崔天昱, 等. 螺旋桨滑流对高升力构型影响的数值计算[J]. 空气动力学学报, 2025, 43(5): 41−50. DOI： 10.7638/kqdlxxb-2024.0090

YANG Longyuan, SHENG Yunyi, CUI Tianyu, et al. Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations[J]. 2025, 43(5): 41-50. DOI： 10.7638/kqdlxxb-2024.0090.

摘要

为了快速、准确分析螺旋桨滑流对增升装置的影响，采用实桨非定常方法（full blades method

FBM）和定常动量激励盘方法（actuator disk method

ADM），数值计算分析了前进比

= 0.7、1.0，攻角

= –4°～24°工况下螺旋桨滑流对高升力构型的影响。研究表明：虽然从单独螺旋桨获取的时均化激励盘载荷分布与从高升力构型螺旋桨获取的存在局部差异，但将来源不同的激励盘载荷应用于ADM计算时，所得高升力构型的压力分布、升阻力结果基本一致，全机升力系数差异不超过4.3%，阻力系数偏差小于5.4%，说明采用单独螺旋桨获取激励盘载荷对全机气动力计算影响不大，从而避免了复杂的网格生成。ADM将非定常计算转化为定常计算，在保持网格量相当（

3300

万）的条件下，其计算结果与FBM结果在失速前（

＜20°时）基本吻合，同时计算核时约降低至FBM的1/18（170/

3100

）。因此 ADM方法能够高效、合理评估出螺旋桨滑流对增升装置产生的影响。

Abstract

To achieve rapid and accurate analysis of propeller slipstream effects on high-lift configurations

this study employed both the full blades method (FBM) and actuator disk method (ADM) for numerical simulations under advance ratios

= 0.7

1.0 and angles of attack ranging from –4° to 24°. The results showed that although there were local differences in time-averaged actuator disk load distrib

utions between isolated propellers and propellers integrated with high-lift configurations

the pressure distributions and lift/drag results obtained by applying these different load sources in ADM calculations were fundamentally consistent. The differences in overall lift coefficient did not exceed 4.3%

and drag coefficient deviations remain below 5.4%

demonstrating that using actuator disk loads from isolated propellers had minimal impact on full-aircraft aerodynamic calculations

thereby avoiding complex grid generation. By converting unsteady computations to steady-state solutions while maintaining equivalent grid resolution (33 million cells)

ADM achieved results that closely match FBM before stall (

＜ 20°)

with computational time reduced to approximately 1/18 of FBM (170 vs.

3100

core-hours). The ADM method thus provides an efficient and reasonable approach for evaluating propeller slipstream effects on high-lift devices.

关键词

Keywords

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